EP2232147B1 - Burner and method for reducing self-induced flame oscillations - Google Patents

Burner and method for reducing self-induced flame oscillations Download PDF

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Publication number
EP2232147B1
EP2232147B1 EP08749689.9A EP08749689A EP2232147B1 EP 2232147 B1 EP2232147 B1 EP 2232147B1 EP 08749689 A EP08749689 A EP 08749689A EP 2232147 B1 EP2232147 B1 EP 2232147B1
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EP
European Patent Office
Prior art keywords
fluid
jet nozzle
fluid inlet
burner
mass flow
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EP08749689.9A
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German (de)
French (fr)
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EP2232147A1 (en
Inventor
Matthias Hase
David Barkowski
Werner Krebs
Berthold Köstlin
Martin Lenze
Martin Stapper
Jaap Van Kampen
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Siemens AG
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Siemens AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a method for reducing self-induced flame vibrations and a burner with which this method can be carried out.
  • Self-induced flame vibrations often occur in combustion chambers and are referred to in this context as Brennschbrummen.
  • a feedback between pressure changes in the combustion chamber and mass flow fluctuations of fuel and air are responsible.
  • the combustion chamber vibrations are an undesirable side effect of the combustion process, since they cause an increased mechanical and thermal loading of the burner components and the combustion chamber components.
  • the combustion chamber hum caused an increased noise in the environment of the respective combustion chamber.
  • a burner in which, in view of stable combustion of a lean premix gas, the fuel and the air are mixed prior to combustion such that separately supplied fuel is mixed with air having a first air ratio in a first device and in a second device for premixing fuel with air to an additional gas mixture having a smaller air ratio than the first air ratio is mixed and the additional gas mixture is annularly injected around the first gas mixture in the combustion chamber.
  • the DE 28 56 399 A1 discloses a burner in which fuel is injected into an air supply pipe to achieve a very fine fuel mist and a controlled distribution of the fuel in the air and immediately downstream of this fuel injection air is injected under high pressure.
  • a method and apparatus for mixing two gaseous reactants are known.
  • a first gas is injected via a nozzle at one end of the mixer.
  • a second gas is introduced into the mixer, the further openings being mounted in different rings on the mixer.
  • a reduction in the combustion chamber humming or a minimization of self-induced flame vibrations has been achieved in part by using Helmholtz resonators.
  • Another possibility is to supply the burner used an increased pilot gas quantity. Pilot gas or pilot fuel is usually used to stabilize the flame. However, an increased supply of pilot gas also leads to increased NO x emissions.
  • the first object is achieved by a method according to claim 1 and claim 2.
  • the second task is by a Burner according to claim 11 and 12 solved.
  • the dependent claims contain further, advantageous embodiments of the invention.
  • a second fluid mass flow is injected into a first fluid mass flow which flows through a jet nozzle from a fluid inlet opening to a fluid outlet opening at at least one axial flow position of the jet nozzle downstream of the fluid inlet opening.
  • a third fluid mass flow branched off in advance from the first fluid mass flow is injected into the first fluid mass flow at a plurality of positions of the circumference of the jet nozzle which are offset relative to one another in the axial direction.
  • the other fluid mass flow includes a fuel.
  • the response behavior for example of the fuel mass flow
  • resonance can only occur for a small proportion of the mass flow.
  • the inventive method can be implemented in particular in the operation of a jet burner, wherein the positive properties of a jet burner are maintained.
  • the second fluid mass flow is injected at at least one radial position of the jet nozzle with respect to the circumference of the jet nozzle. This achieves, as already described above, also the smearing of the delay time between injection and combustion.
  • different radial fuel distributions are realized.
  • the inner areas ie the areas which show to the center of a case to go fatter.
  • flame extinction and CO emissions can be prevented.
  • the fluid mass flow comprising a fuel can be, for example, an air-fuel mixture.
  • the fuel used may in particular be gaseous fuel, for example natural gas or a synthesis gas. Since for natural gas, the fuel mass flows are significantly lower than the air mass flows, even in the case of injection perpendicular to the flow direction of the air is not expected to increase significantly the pressure loss. Furthermore, the method can also be applied to liquid fuels.
  • the second and / or the third fluid mass flow can be injected into the first fluid mass flow at an angle between 0 ° and 90 °.
  • the second fluid mass flow may be injected into the first fluid mass flow at an angle of 90 ° and the third fluid mass flow may be injected into the first fluid mass flow at an angle of 45 °.
  • the advantage of jet-in-cross flow injection is a contribution to increased mixing of the air-fuel mixture, while wall film formation is primarily a measure against flashback.
  • the burner according to the invention comprises at least one jet nozzle with a fluid main inlet opening and a fluid outlet opening, the main fluid inlet opening being connected to a first fluid supply line, at least one fluid secondary inlet opening being connected to a second fluid supply line at at least one axial axial position of the jet nozzle relative to the main fluid inlet opening , is arranged.
  • the burner according to the invention is characterized in that secondary fluid inlet openings are connected to the first fluid line and arranged at a plurality of positions offset in the axial direction relative to one another along the circumference of the jet nozzle.
  • the burner according to the invention comprises at least one jet nozzle having a main fluid inlet opening and a fluid outlet opening, the main fluid inlet opening being connected to a first fluid supply line, at least one fluid secondary inlet opening being connected to a second fluid supply line at at least one radial position of the jet nozzle relative to the circumference of the jet nozzle is connected, is arranged.
  • the alternative form of the burner according to the invention is likewise characterized in that secondary fluid inlet openings are connected to the first fluid line and are arranged at a plurality of positions arranged offset to one another in the axial direction along the circumference of the jet nozzle.
  • the fluid sub-inlet openings and the main fluid inlet opening can each have a central axis.
  • the center axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to the central axis of the main fluid inlet opening and / or to the center axis of the jet nozzle.
  • the center axes of a first part of the fluid sub-inlet ports may be at 90 ° to the central axis of the main fluid inlet port and / or the central axis of the jet nozzle and the central axes of a second portion of the fluid sub-inlet ports may be at 45 ° to the central axis of the main fluid inlet port and / or the central axis of the Have jet nozzle.
  • the fluid sub-inlet openings and the main fluid inlet opening may each have a central axis and the central axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to a radial direction with respect to the central axis of the main fluid inlet opening.
  • This can be injected tangentially along the circumference of the jet nozzle and in this way a wall film can be produced on the inner surface of the jet nozzle.
  • An injection along the circumference of the jet nozzle can also be used to generate vortices in the jet nozzle.
  • a plurality of fluid supply lines connected to fluid side inlet openings may be connected to one another via a ring distributor arranged along the circumference of the jet nozzle.
  • a fuel nozzle can be arranged in the main fluid inlet opening or directly in front of the main fluid inlet opening.
  • the fuel nozzle may include a fuel distributor disposed in or immediately in front of the main fluid inlet port.
  • At least one secondary fluid inlet opening may be designed as an annular gap extending along the circumference of the jet nozzle.
  • the burner according to the invention may comprise a plurality of jet nozzles, wherein the annular gaps of the various jet nozzles are arranged at respectively different axial positions.
  • the burner according to the invention may comprise a plurality of, for example, annularly arranged with respect to the central axis of the burner, jet nozzles. It may further include one or more pilot burners.
  • the burner according to the invention is preferably used in a gas turbine.
  • FIG. 1 schematically shows a section through a jet burner 1 perpendicular to a central axis 4 of the burner 1.
  • the burner 1 comprises a housing 6 which has a circular cross-section. Within the housing 6 a certain number of jet nozzles 2 is arranged substantially annular. Each jet nozzle 2 has a circular cross section.
  • the burner 1 may comprise a pilot burner.
  • FIG. 2 schematically shows a section through a jet burner 101, wherein the section perpendicular to the central axis of the burner 101 runs.
  • the burner 101 also has a housing 6, which has a circular cross section and in which a number of inner and outer jet nozzles 2, 3 is arranged.
  • the jet nozzles 2, 3 each have a circular cross-section, wherein the outer jet nozzles 2 have an equal or larger cross-sectional area than the inner jet nozzles 3.
  • the outer jet nozzles 2 are arranged substantially annularly within the housing 6 and form an outer ring.
  • the inner jet nozzles 3 are also arranged annularly within the housing 6.
  • the inner jet nozzles 3 form an inner ring, which is arranged concentrically to the outer jet nozzle ring.
  • FIGS. 1 and 2 merely show examples of the arrangement of jet nozzles 2, 3 within a jet burner 1, 101. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 2, 3 are possible.
  • FIG. 3 schematically shows a section through a portion of a jet burner 1 in the longitudinal direction, ie along the central axis 4 of the burner 1.
  • the burner 1 has at least one arranged in a housing 6 jet nozzle 2.
  • the central axis of the jet nozzle 2 is indicated by the reference numeral 5.
  • the jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9.
  • the combustion chamber 18 adjoins the fluid outlet opening 9.
  • the jet nozzle 2 is arranged in the housing 6 such that the main fluid inlet opening 8 faces the rear wall 24 of the burner 1.
  • the housing 6 further comprises a radially outer housing part 27 with respect to the central axis 4 of the burner 1.
  • the jet nozzle 2 is fluidically connected to a compressor. Coming from the compressor compressed air is passed through an annular gap 22 to the main fluid inlet 8 and / or radially via an air inlet opening 23 in relation directed to the central axis 5 of the jet nozzle 2 to the fluid main inlet 8.
  • the compressed air flows through the annular gap 22 in the direction of the arrow indicated by the reference numeral 15, ie parallel to the central axis 5 of the jet nozzle 2.
  • the in the direction of arrow 15th flowing air is then deflected at the rear wall 24 of the burner 1 by 180 ° and then flows through the main fluid inlet 8 into the jet nozzle 2.
  • the flow direction of the air within the jet nozzle 2 is indicated by an arrow 10.
  • the compressed air coming from the compressor can also be supplied through an opening 23 which is arranged in the housing 6 of the burner 1 radially with respect to the central axis 5 of the jet nozzle 2.
  • the flow direction of the compressed air flowing through the opening 23 is indicated by an arrow 26.
  • the compressed air is then deflected by 90 ° and then flows through the main fluid inlet 8 into the jet nozzle. 2
  • the burner 1 can also be designed without the outer housing part 27 or without the outer housing 27.
  • the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8.
  • the burner 1 according to the invention can furthermore be designed without the rear wall 24.
  • the jet nozzle 2 is surrounded radially by a ring distributor 7, which is supplied with fuel 12 via a fuel feed line 13.
  • the annular distributor 7 has a number of fluid secondary inlet openings 14, through which fuel can be injected into the air mass flow flowing through the jet nozzle 2.
  • the fluid sub-inlet openings 14 may be designed as a slot or oval nozzle. This is particularly advantageous from synthesis gas injection, since thus the air flow a smaller inflow area is offered. This also results in a lower tendency for recirculation behind the fuel injection.
  • the direction of flow of the fuel 12 injected into the jet nozzle 2 through the fluid sub-inlet openings 14 is indicated by arrows 17.
  • the flow direction 17 of the injected fuel 12 extends perpendicular to the central axis 5 of the jet nozzle 2 and thus also perpendicular to the main flow direction 10 of the compressed air 11 flowing through the jet nozzle 2.
  • Fluid side inlet openings 14 are arranged at three different axial positions, wherein at each axial position in each case two fluid side inlet openings 14 are arranged opposite to each other.
  • a number of fluid sub-inlet openings 14 are arranged along the circumference of the jet nozzle 2. These can in particular also be arranged axially offset from one another.
  • secondary fluid inlet openings 14 may be arranged at only one or at further axial positions along the circumference of the jet nozzle 2.
  • FIG. 4 schematically shows a section through a burner 201 according to the invention, which is a further development of in the FIG. 3 shown burner 1 represents.
  • the compressed air 11 coming from a compressor can in turn be supplied to the jet nozzle 2 either via an annular gap 22 or, as shown in FIG. 3, via an air inlet opening perpendicular to the central axis 5 of the jet nozzle.
  • the compressed air 11 is supplied via an annular gap 22 of the jet nozzle 2.
  • the injection perpendicular to the central axis 5 is therefore indicated only by a dashed arrow 26.
  • burner 201 in addition to the fluid sub-inlet openings 14, is injected through the fuel in the jet nozzle 2, further fluid side inlet openings 25, is injected through the additional compressed air in the flow direction indicated by arrows 16 in the jet nozzle 2.
  • additional fluid sub-inlet openings 25 are connected to the annular gap 22. This means that part of the compressed air coming from the compressor 11 is passed through the annular gap 22 to the rear wall 24 of the burner, where it is deflected by 180 ° and then passes through the main fluid inlet opening 8 into the jet nozzle 2. This air mass flow flows through the jet nozzle 2 in the direction indicated by an arrow 10 direction.
  • the fluid sub-inlet openings 25 can be arranged at different axial positions of the jet nozzle 2.
  • the fluid secondary inlet openings 25, through which compressed air is injected into the jet nozzle 2 are arranged such that a fluid secondary inlet opening 25 is arranged downstream of a fluid secondary inlet opening 14 through which fuel 12 is injected into the jet nozzle 2 in the flow direction 10 downstream.
  • the fluid sub-inlet openings 25 are arranged offset radially along the circumference of the jet nozzle 2. In this way, the flow is not always weakened at the same circumferential position.
  • the fluid side inlet openings 14 and 25 are arranged such that the fuel 12 is injected through the fluid secondary inlet openings 14 perpendicular to the flow direction 10 of the compressed air 11 flowing through the main fluid inlet opening 8 into the jet nozzle 2. Further compressed air is injected into the jet nozzle 2 through the fluid sub-inlet openings 25 at an angle of about 45 ° to the main flow direction 10. Both the fuel 12 and the additional compressed air can be injected at any other angle between 0 ° and 90 ° to the main flow direction 10 at different axial positions in the jet nozzle 2. Since, for example, for natural gas, the fuel mass flows are significantly lower than the air mass flows, no significant increase in the pressure loss is to be expected even in the case of a vertical fuel injection. The fuel 12 can also be injected counter to the air flow direction 10.
  • the fuel can be supplied via one or more fuel supply lines 13 and transported via a ring distributor 7 to the individual jet nozzles 2.
  • these can advantageously be arranged along the circumference of the burner. It is also advantageous if the injection of the fuel into the air jet at more than one axial position of the jet pipe 2 is completed. In addition, for a better mixing at several circumferential positions of the jet pipe 2 can be injected.
  • FIGS. 5 to 7 each show sections through a portion of a burner 301 along the central axis 4 of the burner 301.
  • the burner 301 has at least one, but advantageously a plurality, substantially annularly arranged around the central axis 4 jet nozzles 2. With respect to possible arrangements of the jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.
  • a fuel nozzle 19 is arranged.
  • fuel 12 is injected into the jet nozzle 2.
  • the fuel 12 is preferably injected at an angle of approximately 45 ° to the flow direction 10 of the compressed air 11 flowing into the jet nozzle through the main fluid inlet opening 8.
  • the flow direction of the injected fuel nozzle 19 through the fuel 12 is indicated by arrows 17.
  • the fuel 12 can also be injected at a different angle between 0 ° and 90 ° to the flow direction 10 of the compressed air 11 in the jet nozzle 2.
  • the compressed air coming from a compressor is injected through an air inlet opening 23 perpendicular to the central axis 5 of the jet nozzle 2 in the burner 301.
  • the flow direction of the opening 23 passing compressed air 11 is indicated by an arrow 26.
  • the compressed air 11 now flows through the annular gap 22 to the fluid sub-inlet openings 25 and passes through them into the jet nozzle 2.
  • the majority of the compressed air 11 is introduced into the jet nozzle 2 through the main fluid inlet opening 8 in the flow direction 10.
  • FIG. 7 shows an alternative embodiment of the in the FIG. 5 shown burner 301.
  • the fluid sub-inlet openings 25 are arranged in that the compressed air injected into the jet nozzle 2 through the secondary fluid inlet openings 25 is injected into the compressed air at an angle of approximately 45 ° to the central axis 5 of the jet tube 2.
  • another Eindüswinkel between 0 ° and 90 ° is possible and useful.
  • the air used for the axially stepped Heileindüsung of the present embodiment can be removed either from the annular gap 22 or directly from a surrounding the burner 301 plenum and are injected into the fuel-air mixture in the jet nozzle.
  • the air can be introduced as a jet in the cross flow or as a wall film.
  • the advantage of jet-in-cross-flow injection is a contribution to increased mixing of the fuel-air mixture, while wall-film formation is primarily a measure against potential flashback.
  • the air can be injected tangentially with respect to the circumference of the jet nozzle 2 in this. In this case, a wall film can be produced on the entire inner surface of the jet nozzle 2. Tangential injection can also be used to generate turbulence in the jet nozzle 2.
  • jet-in-cross-flow injection with a wall-film injection by arranging the nozzles very shortly after one another.
  • the jet-in-cross flow injection provides for improved mixing, especially in the core region of the jet, and the film of the second jet strengthens the flow boundary layer and thus prevents flashback.
  • This embodiment is particularly advantageous for a central co-flow injection in the Hauptbrennscherindüsung, for example for synthesis gas. With a high proportion of air in the axial staging, it is possible to adjust the nozzle diameter of the jet nozzle so that the flow velocity in the nozzle remains substantially the same.
  • FIGS. 8 and 9 schematically show various variants of a burner 401 longitudinally along the central axis 4 of the burner 401.
  • the burner 401 has a number of jet nozzles 2, which are arranged substantially annularly around the central axis 4 of the burner 401.
  • jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.
  • Each jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9.
  • the fluid outlet opening 9 opens into the combustion chamber 18.
  • a fuel nozzle 19 is arranged in the main fluid inlet opening 8.
  • the fuel nozzle 19 comprises a fuel distributor 20 with the aid of which fuel 12 can be injected into the jet nozzle 2 at different radial positions and different circumferential positions of the main fluid inlet opening 8.
  • the flow direction of the injected fuel 12 is indicated by arrows 17.
  • annular gap 21 is arranged at a further downstream with respect to the flow directions 10 and 17 located axial position of the jet nozzle 2. Air is injected into the jet nozzle 2 through the annular gap 21. The direction of flow of the injected air is indicated by arrows 16. The air is injected almost parallel to the central axis 5 of the jet nozzle 2 in this. Unlike the one in the FIG. 8 shown variant is in the FIG. 9 the annular gap 21 is disposed at a position further downstream of the main fluid inlet port 8. In both in the FIGS.
  • the compressed air used can be directed by a compressor either through an annular gap 22 in the flow direction 15 to the main fluid inlet opening 8 of the jet nozzle 2 and / or vertically be injected to the central axis 5 in the flow direction 26.
  • FIGS. 8 and 9 embodiments shown include the possibility of the downstream with respect to the flow direction 15 of the compressed air from the compressor located nozzle part, which also depends on the fuel distribution, stuck from the rear wall 24 of the burner in the burner 401 and this through the front, combustion chamber side part to position, for example by spacers in the annulus. In extreme cases, the downstream nozzle part sits directly in the bottom of the flame tube.
  • the Fig. 10 shows a cross section of a steel burner 1 and the ring manifold 7 with a plurality of radial fluid sub-inlet openings 14. The ring manifold 7 thereby comprises a complete ring of jet nozzles 2.
  • the burner 201, 301, 401 according to the invention can also be designed without the outer housing part 27 or without the outer housing 27 in all exemplary embodiments and variants.
  • the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8.
  • the burner 1, 101, 201, 301, 401 according to the invention can furthermore be designed without the rear wall 24.
  • annular gaps 21 By varying the axial positions of the annular gaps 21, an additional design parameter against thermoacoustic flame oscillations is obtained. It is also possible to provide the different jet nozzles 2 of a burner 401 with annular gaps 21 at different axial positions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)

Description

Die vorliegende Erfindung betrifft ein Verfahren zur Verringerung von selbstinduzierten Flammenschwingungen und einen Brenner, mit dem dieses Verfahren durchgeführt werden kann.The present invention relates to a method for reducing self-induced flame vibrations and a burner with which this method can be carried out.

Selbstinduzierte Flammenschwingungen treten vielfach in Brennkammern auf und werden in diesem Zusammenhang auch als Brennkammerbrummen bezeichnet. Für die Ausbildung von Brennkammerschwingungen sind eine Rückkopplung zwischen Druckänderungen in der Brennkammer und Massenstromschwankungen von Brennstoff und Luft verantwortlich. Die Brennkammerschwingungen stellen einen unerwünschten Nebeneffekt des Verbrennungsvorganges dar, da sie eine erhöhte mechanische und thermische Belastung der Brennerbauteile und der Brennkammerbauteile bewirken. Zudem verursacht das Brennkammerbrummen eine erhöhte Lärmbelastung in der Umgebung der jeweiligen Brennkammer.Self-induced flame vibrations often occur in combustion chambers and are referred to in this context as Brennkammerbrummen. For the formation of combustion chamber vibrations, a feedback between pressure changes in the combustion chamber and mass flow fluctuations of fuel and air are responsible. The combustion chamber vibrations are an undesirable side effect of the combustion process, since they cause an increased mechanical and thermal loading of the burner components and the combustion chamber components. In addition, the combustion chamber hum caused an increased noise in the environment of the respective combustion chamber.

Aus der US 5 339 635 ist beispielsweise ein Brenner bekannt, bei dem im Hinblick auf eine stabile Verbrennung eines mageren Vormischgases der Brennstoff und die Luft vor der Verbrennung derart vermischt werden, dass in einer ersten Einrichtung getrennt zugeführter Brennstoff mit Luft mit einem ersten Luftverhältnis gemischt wird und in einer zweiten Einrichtung zum Vormischen von Brennstoff mit Luft zu einem Zusatz-Gasgemisch mit einem kleineren Luftverhältnis als das erste Luftverhältnis gemischt wird und das Zusatz-Gasgemisch ringförmig um das erste Gasgemisch in die Brennkammer eindüsbar ist.From the US 5,339,635 For example, a burner is known in which, in view of stable combustion of a lean premix gas, the fuel and the air are mixed prior to combustion such that separately supplied fuel is mixed with air having a first air ratio in a first device and in a second device for premixing fuel with air to an additional gas mixture having a smaller air ratio than the first air ratio is mixed and the additional gas mixture is annularly injected around the first gas mixture in the combustion chamber.

Die DE 28 56 399 A1 offenbart einen Brenner, bei dem zur Erreichung eines sehr feinen Brennstoffnebels und einer kontrollierten Verteilung des Brennstoffs in der Luft, in ein Luftzufuhrrohr Brennstoff eingedüst wird und unmittelbar stromab dieser Brennstoffeindüsung Luft unter Hochdruck eingedüst wird.The DE 28 56 399 A1 discloses a burner in which fuel is injected into an air supply pipe to achieve a very fine fuel mist and a controlled distribution of the fuel in the air and immediately downstream of this fuel injection air is injected under high pressure.

Aus der US 2004/231586 sind ein Verfahren und eine Vorrichtung zum Mischen zweier gasförmiger Reaktionspartner bekannt. Über eine Düse am einen Ende des Mischers wird ein erstes Gas eingedüst. Über weitere, in die Wand des Mischers gebohrte Öffnungen, wird ein zweites Gas in den Mischer eingebracht, wobei die weiteren Öffnungen in verschiedenen Ringen am Mischer angebracht sind.From the US 2004/231586 For example, a method and apparatus for mixing two gaseous reactants are known. A first gas is injected via a nozzle at one end of the mixer. Via further openings drilled in the wall of the mixer, a second gas is introduced into the mixer, the further openings being mounted in different rings on the mixer.

Eine Verringerung des Brennkammerbrummens beziehungsweise eine Minimierung von selbstinduzierten Flammenschwingungen wird bisher teilweise mithilfe von Helmholtz-Resonatoren erreicht. Eine weitere Möglichkeit besteht darin, dem verwendeten Brenner eine erhöhte Pilotgasmenge zuzuführen. Pilotgas beziehungsweise Pilotbrennstoff wird üblicherweise zur Stabilisierung der Flamme eingesetzt. Eine erhöhte Zuführung von Pilotgas führt allerdings auch zu erhöhten NOx-Emissionen.A reduction in the combustion chamber humming or a minimization of self-induced flame vibrations has been achieved in part by using Helmholtz resonators. Another possibility is to supply the burner used an increased pilot gas quantity. Pilot gas or pilot fuel is usually used to stabilize the flame. However, an increased supply of pilot gas also leads to increased NO x emissions.

Es ist daher eine Aufgabe der vorliegenden Erfindung, ein vorteilhaftes Verfahren zur Verringerung von selbstinduzierten Flammenschwingungen zur Verfügung zu stellen. Es ist eine weitere Aufgabe der vorliegenden Erfindung, einen vorteilhaften Brenner zur Verfügung zu stellen.It is therefore an object of the present invention to provide an advantageous method for reducing self-induced flame vibrations. It is another object of the present invention to provide an advantageous burner.

Die erste Aufgabe wird durch ein Verfahren nach Anspruch 1 und Anspruch 2 gelöst. Die zweite Aufgabe wird durch einen Brenner nach Anspruch 11 und 12 gelöst. Die abhängigen Ansprüche beinhalten weitere, vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by a method according to claim 1 and claim 2. The second task is by a Burner according to claim 11 and 12 solved. The dependent claims contain further, advantageous embodiments of the invention.

In dem erfindungsgemäßen Verfahren zur Verringerung von selbstinduzierten Flammenschwingungen wird in einen ersten Fluidmassenstrom, der eine Strahldüse von einer Fluideinlassöffnung zu einer Fluidauslassöffnung durchströmt, an mindestens einer in Bezug auf die Fluideinlassöffnung stromabwärts gelegenen axialen Position der Strahldüse ein zweiter Fluidmassenstrom eingedüst. Zusätzlich wird ein zuvor vom ersten Fluidmassenstrom abgezweigter dritter Fluidmassenstrom an mehreren in axialer Richtung zueinander versetzt angeordneten Position des Umfanges der Strahldüse in den ersten Fluidmassenstrom eingedüst. Von den ersten und zweiten Fluidmassenströmen umfasst dabei einer Luft. Der andere Fluidmassenstrom umfasst einen Brennstoff. Indem der Brennstoff und/oder die Luft an mehreren axialen Positionen in einen die Strahldüse durchströmenden Hauptfluidmassenstrom eingedüst wird, wird das Antwortverhalten zum Beispiel des Brennstoffmassenstroms so verschmiert, dass sich eine Resonanz nur noch für einen geringen Anteil des Massenstroms einstellen kann. Durch das erfindungsgemäße Verfahren wird eine Verschmierung der Verzögerungszeit zwischen Eindüsung und Verbrennung erreicht. Das erfindungsgemäße Verfahren kann insbesondere bei dem Betrieb eines Strahlbrenners umgesetzt werden, wobei die positiven Eigenschaften eines Strahlbrenners erhalten bleiben.In the method according to the invention for reducing self-induced flame oscillations, a second fluid mass flow is injected into a first fluid mass flow which flows through a jet nozzle from a fluid inlet opening to a fluid outlet opening at at least one axial flow position of the jet nozzle downstream of the fluid inlet opening. In addition, a third fluid mass flow branched off in advance from the first fluid mass flow is injected into the first fluid mass flow at a plurality of positions of the circumference of the jet nozzle which are offset relative to one another in the axial direction. Of the first and second fluid mass flows thereby includes an air. The other fluid mass flow includes a fuel. By injecting the fuel and / or the air at several axial positions into a main fluid mass flow flowing through the jet nozzle, the response behavior, for example of the fuel mass flow, is so smeared that resonance can only occur for a small proportion of the mass flow. By the method according to the invention, a smearing of the delay time between injection and combustion is achieved. The inventive method can be implemented in particular in the operation of a jet burner, wherein the positive properties of a jet burner are maintained.

Alternativ oder zusätzlich wird der zweite Fluidmassenstrom an mindestens einer in Bezug auf den Umfang der Strahldüse gelegenen radialen Position der Strahldüse eingedüst.
Dies erreicht, wie oben bereits beschrieben, ebenfalls die Verschmierung der Verzögerungszeit zwischen Eindüsung und Verbrennung.Alternatively or additionally, the second fluid mass flow is injected at at least one radial position of the jet nozzle with respect to the circumference of the jet nozzle.
This achieves, as already described above, also the smearing of the delay time between injection and combustion.

Bevorzugt werden unterschiedliche radiale Brennstoffverteilungen realisiert. Hier ist es z.B. im Teillastbetrieb von Vorteil die inneren Bereiche, d.h. den Bereichen welche zur Mitte eines Gehäuses zeigen, fetter zu fahren. Somit können Flammenverlöschen und CO-Emissionen vorgebeugt werden.Preferably, different radial fuel distributions are realized. Here, for example, it is advantageous in partial load operation, the inner areas, ie the areas which show to the center of a case to go fatter. Thus, flame extinction and CO emissions can be prevented.

Bei dem einen Brennstoff umfassenden Fluidmassenstrom kann es sich beispielsweise um ein Luft-Brennstoff-Gemisch handeln. Bei dem verwendeten Brennstoff kann es sich insbesondere um gasförmigen Brennstoff, beispielsweise um Erdgas oder um ein Synthesegas, handeln. Da für Erdgas die Brennstoffmassenströme deutlich geringer sind als die Luftmassenströme, ist auch im Falle einer Eindüsung senkrecht zur Strömungsrichtung der Luft nicht mit einer signifikanten Erhöhung des Druckverlustes zu rechnen. Des Weiteren kann das Verfahren auch auf flüssige Brennstoffe angewandt werden.The fluid mass flow comprising a fuel can be, for example, an air-fuel mixture. The fuel used may in particular be gaseous fuel, for example natural gas or a synthesis gas. Since for natural gas, the fuel mass flows are significantly lower than the air mass flows, even in the case of injection perpendicular to the flow direction of the air is not expected to increase significantly the pressure loss. Furthermore, the method can also be applied to liquid fuels.

Vorzugsweise können der zweite und/oder der dritte Fluidmassenstrom in einem Winkel zwischen 0° und 90° in den ersten Fluidmassenstrom eingedüst werden. Zum Beispiel kann der zweite Fluidmassenstrom in einem Winkel von 90° in den ersten Fluidmassenstrom eingedüst werden und der dritte Fluidmassenstrom in einem Winkel von 45° in den ersten Fluidmassenstrom eingedüst werden. Der Vorteil der Strahl-in-Querströmungseindüsung ist ein Beitrag zu einer erhöhten Mischung des Luft-Brennstoff-Gemisches, während eine Wandfilmbildung vor allem eine Maßnahme gegen Flammenrückschlag ist.Preferably, the second and / or the third fluid mass flow can be injected into the first fluid mass flow at an angle between 0 ° and 90 °. For example, the second fluid mass flow may be injected into the first fluid mass flow at an angle of 90 ° and the third fluid mass flow may be injected into the first fluid mass flow at an angle of 45 °. The advantage of jet-in-cross flow injection is a contribution to increased mixing of the air-fuel mixture, while wall film formation is primarily a measure against flashback.

Der erfindungsgemäße Brenner umfasst mindestens eine Strahldüse mit einer Fluidhaupteinlassöffnung und einer Fluidauslassöffnung, wobei die Fluidhaupteinlassöffnung mit einer ersten Fluidzuleitung verbunden ist, wobei an mindestens einer in Bezug auf die Fluidhaupteinlassöffnung stromabwärts gelegenen axialen Position der Strahldüse mindestens eine Fluidnebeneinlassöffnung, die mit einer zweiten Fluidzuleitung verbunden ist, angeordnet ist. Der erfindungsgemäße Brenner ist dadurch gekennzeichnet, dass Fluidnebeneinlassöffnungen mit der ersten Fluidleitung verbunden und an mehreren in axialer Richtung zueinander versetzt angeordneten Positionen entlang des Umfanges der Strahldüse angeordnet sind.The burner according to the invention comprises at least one jet nozzle with a fluid main inlet opening and a fluid outlet opening, the main fluid inlet opening being connected to a first fluid supply line, at least one fluid secondary inlet opening being connected to a second fluid supply line at at least one axial axial position of the jet nozzle relative to the main fluid inlet opening , is arranged. The burner according to the invention is characterized in that secondary fluid inlet openings are connected to the first fluid line and arranged at a plurality of positions offset in the axial direction relative to one another along the circumference of the jet nozzle.

Alternativ umfasst der erfindungsgemäße Brenner mindestens eine Strahldüse mit einer Fluidhaupteinlassöffnung und einer Fluidauslassöffnung, wobei die Fluidhaupteinlassöffnung mit einer ersten Fluidzuleitung verbunden ist, wobei an mindestens einer in Bezug auf den Umfang der Strahldüse gelegenen radialen Position der Strahldüse mindestens eine Fluidnebeneinlassöffnung, die mit einer zweiten Fluidzuleitung verbunden ist, angeordnet ist. Die alternative Form des erfindungsgemäßen Brenners ist ebenfalls dadurch gekennzeichnet, dass Fluidnebeneinlassöffnungen mit der ersten Fluidleitung verbunden und an mehreren in axialer Richtung zueinander versetzt angeordneten Positionen entlang des Umfanges der Strahldüse angeordnet sind.Alternatively, the burner according to the invention comprises at least one jet nozzle having a main fluid inlet opening and a fluid outlet opening, the main fluid inlet opening being connected to a first fluid supply line, at least one fluid secondary inlet opening being connected to a second fluid supply line at at least one radial position of the jet nozzle relative to the circumference of the jet nozzle is connected, is arranged. The alternative form of the burner according to the invention is likewise characterized in that secondary fluid inlet openings are connected to the first fluid line and are arranged at a plurality of positions arranged offset to one another in the axial direction along the circumference of the jet nozzle.

Weiterhin können die Fluidnebeneinlassöffnungen und die Fluidhaupteinlassöffnung jeweils eine Mittelachse aufweisen. Dabei können die Mittelachsen der Fluidnebeneinlassöffnungen einen Winkel zwischen 0° und 90° zu der Mittelachse der Fluidhaupteinlassöffnung und/oder zu der Mittelachse der Strahldüse aufweisen. Vorteilhafterweise können die Mittelachsen eines ersten Teiles der Fluidnebeneinlassöffnungen einen Winkel von 90° zu der Mittelachse der Fluidhaupteinlassöffnung und/oder zu der Mittelachse der Strahldüse aufweisen und die Mittelachsen eines zweites Teiles der Fluidnebeneinlassöffnungen einen Winkel von 45° zu der Mittelachse der Fluidhaupteinlassöffnung und/oder zu der Mittelachse der Strahldüse aufweisen. Der Vorteil der Strahl-in-Querströmungseindüsung ist ein Beitrag zu einer erhöhten Mischung des Luft-Brennstoff-Gemisches, während eine Wandfilmbildung vor allem eine Maßnahme gegen Flammenrückschlag ist.Furthermore, the fluid sub-inlet openings and the main fluid inlet opening can each have a central axis. In this case, the center axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to the central axis of the main fluid inlet opening and / or to the center axis of the jet nozzle. Advantageously, the center axes of a first part of the fluid sub-inlet ports may be at 90 ° to the central axis of the main fluid inlet port and / or the central axis of the jet nozzle and the central axes of a second portion of the fluid sub-inlet ports may be at 45 ° to the central axis of the main fluid inlet port and / or the central axis of the Have jet nozzle. The advantage of jet-in-cross-flow injection is a contribution to increased mixing of the air-fuel mixture, while wall-film formation is primarily a flash back-off measure.

Die Fluidnebeneinlassöffnungen und die Fluidhaupteinlassöffnung können jeweils eine Mittelachse aufweisen und die Mittelachsen der Fluidnebeneinlassöffnungen können einen Winkel zwischen 0° und 90° zu einer radialen Richtung in Bezug auf die Mittelachse der Fluidhaupteinlassöffnung aufweisen. Dadurch kann tangential entlang des Umfanges der Strahldüse eingedüst und auf diese Weise ein Wandfilm an der inneren Oberfläche der Strahldüse erzeugt werden. Ein Eindüsen entlang des Umfanges der Strahldüse kann auch zur Erzeugung von Wirbeln in der Strahldüse genutzt werden.The fluid sub-inlet openings and the main fluid inlet opening may each have a central axis and the central axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to a radial direction with respect to the central axis of the main fluid inlet opening. This can be injected tangentially along the circumference of the jet nozzle and in this way a wall film can be produced on the inner surface of the jet nozzle. An injection along the circumference of the jet nozzle can also be used to generate vortices in the jet nozzle.

Mehrere mit Fluidnebeneinlassöffnungen verbundene Fluidzuleitungen können über einen entlang des Umfanges der Strahldüse angeordneten Ringverteiler mit einander verbunden sein.A plurality of fluid supply lines connected to fluid side inlet openings may be connected to one another via a ring distributor arranged along the circumference of the jet nozzle.

Zudem kann eine Brennstoffdüse in der Fluidhaupteinlassöffnung oder unmittelbar vor der Fluidhaupteinlassöffnung angeordnet sein. Die Brennstoffdüse kann einen Brennstoffverteiler umfassen, der in oder unmittelbar vor der Fluidhaupteinlassöffnung angeordnet ist.In addition, a fuel nozzle can be arranged in the main fluid inlet opening or directly in front of the main fluid inlet opening. The fuel nozzle may include a fuel distributor disposed in or immediately in front of the main fluid inlet port.

Mindestens eine Fluidnebeneinlassöffnung kann als entlang des Umfanges der Strahldüse verlaufender Ringspalt ausgestaltet sein. In diesem Fall kann der erfindungsgemäße Brenner mehrere Strahldüsen umfassen, wobei die Ringspalte der verschiedenen Strahldüsen an jeweils unterschiedlichen axialen Positionen angeordnet sind. Durch die Variation der axialen Posi tionen der Ringspalte wird ein zusätzlicher Designparameter gegen thermoakustische Flammenschwingungen gewonnen.At least one secondary fluid inlet opening may be designed as an annular gap extending along the circumference of the jet nozzle. In this case, the burner according to the invention may comprise a plurality of jet nozzles, wherein the annular gaps of the various jet nozzles are arranged at respectively different axial positions. By the variation of the axial Posi An additional design parameter against thermoacoustic flame oscillations is obtained in the ring gaps.

Der erfindungsgemäße Brenner kann mehrere, beispielsweise ringförmig in Bezug auf die Mittelachse des Brenners angeordnete, Strahldüsen umfassen. Er kann einen weiterhin einen oder mehrere Pilotbrenner umfassen.The burner according to the invention may comprise a plurality of, for example, annularly arranged with respect to the central axis of the burner, jet nozzles. It may further include one or more pilot burners.

Bevorzugt wird der erfindungsgemäße Brenner in einer Gasturbine eingesetzt.The burner according to the invention is preferably used in a gas turbine.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung werden im Folgenden anhand von Ausführungsbeispielen unter Bezugnahme auf die beigefügten Figuren näher beschrieben.

  • Fig. 1 zeigt schematisch einen Schnitt durch einen Strahlbrenner quer zu dessen Längsrichtung.
  • Fig. 2 zeigt schematisch einen Schnitt durch einen weiteren Strahlbrenner quer zu dessen Längsrichtung.
  • Fig. 3 zeigt schematisch einen Schnitt durch einen Teil eines nicht erfindungsgemäßen Strahlbrenners in Längsrichtung.
  • Fig. 4 zeigt schematisch einen Schnitt durch einen Teil eines weiteren Strahlbrenners in Längsrichtung.
  • Fig. 5 zeigt schematisch einen Schnitt durch einen Teil eines alternativen Strahlbrenners in Längsrichtung.
  • Fig. 6 zeigt schematisch einen Schnitt in Längsrichtung durch einen weiteren Strahlbrenner.
  • Fig. 7 zeigt schematisch einen Schnitt durch einen Teil eines Strahlbrenners in Längsrichtung.
  • Fig. 8 zeigt schematisch einen Strahlbrenner in Längsrichtung, der einen Ringspalt aufweist.
  • Fig. 9 zeigt schematisch eine alternative Anordnung des Ringspaltes des in der Figur 8 gezeigten Strahlbrenners.
  • Fig. 10 zeigt den Querschnitt eines Stahlbrenners sowie des Ringverteilers mit mehreren radialen Fluidnebeneinlassöffnungen.
Further features, properties and advantages of the present invention will be described in more detail below with reference to exemplary embodiments with reference to the accompanying figures.
  • Fig. 1 schematically shows a section through a jet burner transversely to its longitudinal direction.
  • Fig. 2 schematically shows a section through another jet burner transversely to its longitudinal direction.
  • Fig. 3 schematically shows a section through a portion of a non-inventive jet burner in the longitudinal direction.
  • Fig. 4 schematically shows a section through a part of another jet burner in the longitudinal direction.
  • Fig. 5 schematically shows a section through a portion of an alternative jet burner in the longitudinal direction.
  • Fig. 6 shows schematically a longitudinal section through another jet burner.
  • Fig. 7 schematically shows a section through a portion of a jet burner in the longitudinal direction.
  • Fig. 8 schematically shows a jet burner in the longitudinal direction, which has an annular gap.
  • Fig. 9 schematically shows an alternative arrangement of the annular gap of in the FIG. 8 shown jet burner.
  • Fig. 10 shows the cross section of a steel burner and the annular distributor with several radial fluid secondary inlet openings.

Die Figur 1 zeigt schematisch einen Schnitt durch einen Strahlbrenner 1 senkrecht zu einer Mittelachse 4 des Brenners 1. Der Brenner 1 umfasst ein Gehäuse 6, welches einen kreisförmigen Querschnitt aufweist. Innerhalb des Gehäuses 6 ist eine bestimmte Anzahl an Strahldüsen 2 im Wesentlichen ringförmig angeordnet. Jede Strahldüse 2 weist dabei einen kreisförmigen Querschnitt auf. Außerdem kann der Brenner 1 einen Pilotbrenner umfassen.The FIG. 1 schematically shows a section through a jet burner 1 perpendicular to a central axis 4 of the burner 1. The burner 1 comprises a housing 6 which has a circular cross-section. Within the housing 6 a certain number of jet nozzles 2 is arranged substantially annular. Each jet nozzle 2 has a circular cross section. In addition, the burner 1 may comprise a pilot burner.

Die Figur 2 zeigt schematisch einen Schnitt durch einen Strahlbrenner 101, wobei der Schnitt senkrecht zur Mittelachse des Brenners 101 verläuft. Der Brenner 101 weist ebenfalls ein Gehäuse 6 auf, welches einen kreisförmigen Querschnitt besitzt und in welchem eine Anzahl innerer und äußerer Strahldüsen 2, 3 angeordnet ist. Die Strahldüsen 2, 3 weisen jeweils einen kreisförmigen Querschnitt auf, wobei die äußeren Strahldüsen 2 eine gleich große oder größere Querschnittsfläche besitzen als die inneren Strahldüsen 3. Die äußeren Strahldüsen 2 sind im Wesentlichen ringförmig innerhalb des Gehäuses 6 angeordnet und bilden einen äußeren Ring. Die inneren Strahldüsen 3 sind ebenfalls innerhalb des Gehäuses 6 ringförmig angeordnet. Die inneren Strahldüsen 3 bilden einen inneren Ring, der konzentrisch zu dem äußeren Strahldüsenring angeordnet ist.The FIG. 2 schematically shows a section through a jet burner 101, wherein the section perpendicular to the central axis of the burner 101 runs. The burner 101 also has a housing 6, which has a circular cross section and in which a number of inner and outer jet nozzles 2, 3 is arranged. The jet nozzles 2, 3 each have a circular cross-section, wherein the outer jet nozzles 2 have an equal or larger cross-sectional area than the inner jet nozzles 3. The outer jet nozzles 2 are arranged substantially annularly within the housing 6 and form an outer ring. The inner jet nozzles 3 are also arranged annularly within the housing 6. The inner jet nozzles 3 form an inner ring, which is arranged concentrically to the outer jet nozzle ring.

Die Figuren 1 und 2 zeigen lediglich Beispiele für die Anordnung von Strahldüsen 2, 3 innerhalb eines Strahlbrenners 1, 101. Selbstverständlich sind alternative Anordnungen, ebenso wie die Verwendung einer anderen Anzahl an Strahldüsen 2, 3 möglich.The Figures 1 and 2 merely show examples of the arrangement of jet nozzles 2, 3 within a jet burner 1, 101. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 2, 3 are possible.

Die Figur 3 zeigt schematisch einen Schnitt durch einen Teil eines Strahlbrenners 1 in Längsrichtung, also entlang der Mittelachse 4 des Brenners 1. Der Brenner 1 weist mindestens eine in einem Gehäuse 6 angeordnete Strahldüse 2 auf. Die Mittelachse der Strahldüse 2 ist durch die Bezugsziffer 5 gekennzeichnet. Die Strahldüse 2 umfasst eine Fluidhaupteinlassöffnung 8 und eine Fluidauslassöffnung 9. An die Fluidauslassöffnung 9 schließt sich die Brennkammer 18 an. Zudem ist die Strahldüse 2 so in dem Gehäuse 6 angeordnet, dass die Fluidhaupteinlassöffnung 8 der Rückwand 24 des Brenners 1 zugewandt ist. Das Gehäuse 6 umfasst weiterhin einen radial in Bezug auf die Mittelachse 4 des Brenners 1 äußeren Gehäuseteil 27.The FIG. 3 schematically shows a section through a portion of a jet burner 1 in the longitudinal direction, ie along the central axis 4 of the burner 1. The burner 1 has at least one arranged in a housing 6 jet nozzle 2. The central axis of the jet nozzle 2 is indicated by the reference numeral 5. The jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9. The combustion chamber 18 adjoins the fluid outlet opening 9. In addition, the jet nozzle 2 is arranged in the housing 6 such that the main fluid inlet opening 8 faces the rear wall 24 of the burner 1. The housing 6 further comprises a radially outer housing part 27 with respect to the central axis 4 of the burner 1.

Die Strahldüse 2 ist strömungstechnisch mit einem Kompressor verbunden. Die von dem Kompressor kommende Druckluft wird über einen Ringspalt 22 zur Fluidhaupteinlassöffnung 8 geleitet und/oder über eine Lufteinlassöffnung 23 radial in Bezug auf die Mittelachse 5 der Strahldüse 2 zur Fluidhaupteinlassöffnung 8 geleitet. In dem Fall, dass die Druckluft durch den Ringspalt 22 der Strahldüse 2 zugeführt wird, strömt die komprimierte Luft durch den Ringspalt 22 in Richtung des mit der Bezugsziffer 15 gekennzeichneten Pfeils, also parallel zur Mittelachse 5 der Strahldüse 2. Die in Richtung des Pfeils 15 strömende Luft wird dann an der Rückwand 24 des Brenners 1 um 180° umgelenkt und strömt anschließend durch die Fluidhaupteinlassöffnung 8 in die Strahldüse 2. Die Strömungsrichtung der Luft innerhalb der Strahldüse 2 ist durch einen Pfeil 10 gekennzeichnet.The jet nozzle 2 is fluidically connected to a compressor. Coming from the compressor compressed air is passed through an annular gap 22 to the main fluid inlet 8 and / or radially via an air inlet opening 23 in relation directed to the central axis 5 of the jet nozzle 2 to the fluid main inlet 8. In the event that the compressed air is supplied through the annular gap 22 of the jet nozzle 2, the compressed air flows through the annular gap 22 in the direction of the arrow indicated by the reference numeral 15, ie parallel to the central axis 5 of the jet nozzle 2. The in the direction of arrow 15th flowing air is then deflected at the rear wall 24 of the burner 1 by 180 ° and then flows through the main fluid inlet 8 into the jet nozzle 2. The flow direction of the air within the jet nozzle 2 is indicated by an arrow 10.

Zusätzlich oder alternativ zu einer Zufuhr der Druckluft durch den Ringspalt 22 kann die von dem Kompressor kommende Druckluft auch durch eine Öffnung 23, die in dem Gehäuse 6 des Brenners 1 radial in Bezug auf die Mittelachse 5 der Strahldüse 2 angeordnet ist, zugeleitet werden. Die Strömungsrichtung der durch die Öffnung 23 strömenden Druckluft ist durch einen Pfeil 26 gekennzeichnet. In diesem Fall wird die Druckluft anschließend um 90° umgelenkt und strömt dann durch die Fluidhaupteinlassöffnung 8 in die Strahldüse 2.Additionally or alternatively to a supply of compressed air through the annular gap 22, the compressed air coming from the compressor can also be supplied through an opening 23 which is arranged in the housing 6 of the burner 1 radially with respect to the central axis 5 of the jet nozzle 2. The flow direction of the compressed air flowing through the opening 23 is indicated by an arrow 26. In this case, the compressed air is then deflected by 90 ° and then flows through the main fluid inlet 8 into the jet nozzle. 2

Der Brenner 1 kann grundsätzlich auch ohne den äußeren Gehäuseteil 27 beziehungsweise ohne äußeres Gehäuse 27 ausgestaltet sein. In diesem Fall kann die Druckluft direkt in das "Plenum", also den Bereich zwischen der Rückwand 24 und der Fluidhaupteinlassöffnung 8, strömen. Der erfindungsgemäße Brenner 1 kann weiterhin auch ohne die Rückwand 24 ausgestaltet sein.In principle, the burner 1 can also be designed without the outer housing part 27 or without the outer housing 27. In this case, the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8. The burner 1 according to the invention can furthermore be designed without the rear wall 24.

Die Strahldüse 2 ist radial von einem Ringverteiler 7 umgeben, der über eine Brennstoffzuleitung 13 mit Brennstoff 12 versorgt wird. Der Ringverteiler 7 weist eine Anzahl an Fluidnebeneinlassöffnungen 14 auf, durch welche Brennstoff in den durch die Strahldüse 2 strömenden Luftmassenstrom eingedüst werden kann. Die Fluidnebeneinlassöffnungen 14 können als Schlitz oder ovale Düse ausgeführt sein. Dies ist besonders von Synthesegaseindüsung von Vorteil, da damit der Luftströmung eine kleinere Anströmfläche geboten wird. Hieraus ergibt sich auch eine geringere Tendenz zur Rezirkulation hinter der Brennstoffeindüsung. Die Strömungsrichtung des durch die Fluidnebeneinlassöffnungen 14 in die Strahldüse 2 eingedüsten Brennstoffes 12 ist durch Pfeile 17 gekennzeichnet. Die Strömungsrichtung 17 des eingedüsten Brennstoffes 12 verläuft dabei senkrecht zur Mittelachse 5 der Strahldüse 2 und damit auch senkrecht zur Hauptströmungsrichtung 10 der durch die Strahldüse 2 strömenden Druckluft 11.The jet nozzle 2 is surrounded radially by a ring distributor 7, which is supplied with fuel 12 via a fuel feed line 13. The annular distributor 7 has a number of fluid secondary inlet openings 14, through which fuel can be injected into the air mass flow flowing through the jet nozzle 2. The fluid sub-inlet openings 14 may be designed as a slot or oval nozzle. This is particularly advantageous from synthesis gas injection, since thus the air flow a smaller inflow area is offered. This also results in a lower tendency for recirculation behind the fuel injection. The direction of flow of the fuel 12 injected into the jet nozzle 2 through the fluid sub-inlet openings 14 is indicated by arrows 17. The flow direction 17 of the injected fuel 12 extends perpendicular to the central axis 5 of the jet nozzle 2 and thus also perpendicular to the main flow direction 10 of the compressed air 11 flowing through the jet nozzle 2.

In der Figur 3 sind an drei verschiedenen axialen Positionen Fluidnebeneinlassöffnungen 14 angeordnet, wobei an jeder axialen Position jeweils zwei Fluidnebeneinlassöffnungen 14 einander gegenüberliegend angeordnet sind. Vorteilhafterweise sind eine Anzahl an Fluidnebeneinlassöffnungen 14 entlang des Umfanges der Strahldüse 2 angeordnet. Diese können insbesondere auch axial versetzt zueinander angeordnet sein. Grundsätzlich können Fluidnebeneinlassöffnungen 14 an lediglich einer oder an noch weiteren axialen Positionen entlang des Umfanges der Strahldüse 2 angeordnet sein.In the FIG. 3 Fluid side inlet openings 14 are arranged at three different axial positions, wherein at each axial position in each case two fluid side inlet openings 14 are arranged opposite to each other. Advantageously, a number of fluid sub-inlet openings 14 are arranged along the circumference of the jet nozzle 2. These can in particular also be arranged axially offset from one another. In principle, secondary fluid inlet openings 14 may be arranged at only one or at further axial positions along the circumference of the jet nozzle 2.

Im Inneren der Strahldüse 2 bildet sich durch das Eindüsen des Brennstoffes 12 in die durch die Strahldüse 2 strömende Druckluft 11 ein Brennstoff-Luft-Gemisch aus, welches die Strahldüse 2 durch die Fluidauslassöffnung 9 in Richtung der Brennkammer 18 verlässt.By injecting the fuel 12 into the compressed air 11 flowing through the jet nozzle 2, a fuel-air mixture, which leaves the jet nozzle 2 through the fluid outlet opening 9 in the direction of the combustion chamber 18, forms inside the jet nozzle 2.

Die Figur 4 zeigt schematisch einen Schnitt durch einen erfindungsgemäßen Brenner 201, der eine Weiterentwicklung des in der Figur 3 gezeigten Brenners 1 darstellt. Die von einem Kompressor kommende Druckluft 11 kann der Strahldüse 2 wiederum entweder über einen Ringspalt 22 zugeführt werden oder, wie in der Figur 3 gezeigt ist, über eine Lufteinlassöffnung senkrecht zur Mittelachse 5 der Strahldüse eingedüst werden. Vorzugsweise wird in dieser Ausführungsvariante die Druckluft 11 über einen Ringspalt 22 der Strahldüse 2 zugeführt. Das Eindüsen senkrecht zur Mittelachse 5 ist daher lediglich durch einen gestrichelten Pfeil 26 angedeutet.The FIG. 4 schematically shows a section through a burner 201 according to the invention, which is a further development of in the FIG. 3 shown burner 1 represents. The compressed air 11 coming from a compressor can in turn be supplied to the jet nozzle 2 either via an annular gap 22 or, as shown in FIG. 3, via an air inlet opening perpendicular to the central axis 5 of the jet nozzle. Preferably, in this embodiment, the compressed air 11 is supplied via an annular gap 22 of the jet nozzle 2. The injection perpendicular to the central axis 5 is therefore indicated only by a dashed arrow 26.

Zusätzlich zu den im Zusammenhang mit der Figur 3 bereits beschriebenen Merkmalen weist der in der Figur 4 gezeigte Brenner 201 neben den Fluidnebeneinlassöffnungen 14, durch die Brennstoff in die Strahldüse 2 eingedüst wird, weitere Fluidnebeneinlassöffnungen 25 auf, durch die zusätzliche Druckluft in der durch Pfeile 16 gekennzeichneten Strömungsrichtung in die Strahldüse 2 eingedüst wird. Diese zusätzlichen Fluidnebeneinlassöffnungen 25 sind mit dem Ringspalt 22 verbunden. Das bedeutet, dass ein Teil der vom Kompressor kommenden Druckluft 11 durch den Ringspalt 22 zur Rückwand 24 des Brenners geleitet wird, dort um 180° umgelenkt wird und anschließend durch die Fluidhaupteinlassöffnung 8 in die Strahldüse 2 gelangt. Dieser Luftmassenstrom durchströmt die Strahldüse 2 in Richtung der durch einen Pfeil 10 gekennzeichneten Richtung. Ein anderer Teil der vom Kompressor kommenden Druckluft wird von dem Ringspalt 22 durch die Fluidnebeneinlassöffnungen 25 in Richtung der durch die Pfeile 16 gekennzeichneten Strömungsrichtung in die Strahldüse 2 eingedüst. Die Fluidnebeneinlassöffnungen 25 können dabei an verschiedenen axialen Positionen der Strahldüse 2 angeordnet sein. In der Figur 4 sind die Fluidnebeneinlassöffnungen 25, durch welche Druckluft in die Strahldüse 2 eingedüst wird, so angeordnet, dass jeweils in Strömungsrichtung 10 stromabwärts hinter einer Fluidnebeneinlassöffnung 14, durch die Brennstoff 12 in die Strahldüse 2 eingedüst wird, eine Fluidnebeneinlassöffnung 25 angeordnet ist. Beliebige andere Anordnungen sind selbstverständlich möglich. Es ist allerdings vorteilhaft, wenn die Fluidnebeneinlassöffnungen 25 entlang des Umfanges der Strahldüse 2 radial versetzt angeordnet sind. Auf diese Weise wird die Strömung nicht immer an der gleichen Umfangsposition geschwächt.In addition to those related to the FIG. 3 already described features in the FIG. 4 shown burner 201 in addition to the fluid sub-inlet openings 14, is injected through the fuel in the jet nozzle 2, further fluid side inlet openings 25, is injected through the additional compressed air in the flow direction indicated by arrows 16 in the jet nozzle 2. These additional fluid sub-inlet openings 25 are connected to the annular gap 22. This means that part of the compressed air coming from the compressor 11 is passed through the annular gap 22 to the rear wall 24 of the burner, where it is deflected by 180 ° and then passes through the main fluid inlet opening 8 into the jet nozzle 2. This air mass flow flows through the jet nozzle 2 in the direction indicated by an arrow 10 direction. Another part of the compressed air coming from the compressor is injected from the annular gap 22 through the fluid sub-inlet openings 25 in the direction of the flow direction indicated by the arrows 16 in the jet nozzle 2. The fluid sub-inlet openings 25 can be arranged at different axial positions of the jet nozzle 2. In the FIG. 4 the fluid secondary inlet openings 25, through which compressed air is injected into the jet nozzle 2, are arranged such that a fluid secondary inlet opening 25 is arranged downstream of a fluid secondary inlet opening 14 through which fuel 12 is injected into the jet nozzle 2 in the flow direction 10 downstream. Any other arrangements are of course possible. However, it is advantageous if the fluid sub-inlet openings 25 are arranged offset radially along the circumference of the jet nozzle 2. In this way, the flow is not always weakened at the same circumferential position.

In der Figur 4 sind die Fluidnebeneinlassöffnungen 14 und 25 so angeordnet, dass der Brennstoff 12 durch die Fluidnebeneinlassöffnungen 14 senkrecht zur Strömungsrichtung 10 der durch die Fluidhaupteinlassöffnung 8 in die Strahldüse 2 strömenden Druckluft 11 eingedüst wird. Weitere Druckluft wird durch die Fluidnebeneinlassöffnungen 25 in einem Winkel von etwa 45° zur Hauptströmungsrichtung 10 in die Strahldüse 2 eingedüst. Sowohl der Brennstoff 12 als auch die zusätzliche Druckluft können in einem beliebigen anderen Winkel zwischen 0° und 90° zur Hauptströmungsrichtung 10 an verschiedenen axialen Positionen in die Strahldüse 2 eingedüst werden. Da beispielsweise für Erdgas die Brennstoffmassenströme deutlich geringer sind als die Luftmassenströme, ist auch im Falle einer senkrechten Brennstoffeindüsung nicht mit einer signifikanten Erhöhung des Druckverlustes zu rechnen. Der Brennstoff 12 kann auch entgegen der Luftströmungsrichtung 10 eingedüst werden.In the FIG. 4 the fluid side inlet openings 14 and 25 are arranged such that the fuel 12 is injected through the fluid secondary inlet openings 14 perpendicular to the flow direction 10 of the compressed air 11 flowing through the main fluid inlet opening 8 into the jet nozzle 2. Further compressed air is injected into the jet nozzle 2 through the fluid sub-inlet openings 25 at an angle of about 45 ° to the main flow direction 10. Both the fuel 12 and the additional compressed air can be injected at any other angle between 0 ° and 90 ° to the main flow direction 10 at different axial positions in the jet nozzle 2. Since, for example, for natural gas, the fuel mass flows are significantly lower than the air mass flows, no significant increase in the pressure loss is to be expected even in the case of a vertical fuel injection. The fuel 12 can also be injected counter to the air flow direction 10.

Grundsätzlich kann der Brennstoff über ein oder mehrere Brennstoffzuleitungen 13 zugeführt und über einen Ringverteiler 7 zu den einzelnen Strahldüsen 2 transportiert werden. Im Falle des Vorliegens mehrerer Brennstoffzuleitungen 13 können diese vorteilhafterweise entlang des Umfanges des Brenners angeordnet werden. Es ist weiterhin vorteilhaft, wenn die Eindüsung des Brennstoffes in den Luftstrahl an mehr als einer axialen Position des Strahlrohres 2 vollzogen wird. Zudem kann für eine bessere Durchmischung an mehreren Umfangspositionen des Strahlrohres 2 eingedüst werden.In principle, the fuel can be supplied via one or more fuel supply lines 13 and transported via a ring distributor 7 to the individual jet nozzles 2. In the case of the presence of a plurality of fuel supply lines 13, these can advantageously be arranged along the circumference of the burner. It is also advantageous if the injection of the fuel into the air jet at more than one axial position of the jet pipe 2 is completed. In addition, for a better mixing at several circumferential positions of the jet pipe 2 can be injected.

Im Folgenden wird ein zweites Ausführungsbeispiel anhand der Figuren 5 bis 7 näher beschrieben. Elemente, die Elementen entsprechen, die bereits im ersten Ausführungsbeispiel beschrieben wurden, sind mit denselben Bezugsziffern versehen und werden nicht erneut im Detail beschrieben.In the following, a second embodiment based on the FIGS. 5 to 7 described in more detail. Elements corresponding to elements already described in the first embodiment are given the same reference numerals and will not be described again in detail.

Die Figuren 5 bis 7 zeigen jeweils Schnitte durch einen Teil eines Brenners 301 entlang der Mittelachse 4 des Brenners 301. Der Brenner 301 weist mindestens eine, vorteilhafterweise jedoch mehrere, im Wesentlichen ringförmig um die Mittelachse 4 angeordnete Strahldüsen 2 auf. In Bezug auf mögliche Anordnungen der Strahldüsen 2, 3 wird auf die Figuren 1 und 2 und die in diesem Zusammenhang gemachten Ausführungen verwiesen.The FIGS. 5 to 7 each show sections through a portion of a burner 301 along the central axis 4 of the burner 301. The burner 301 has at least one, but advantageously a plurality, substantially annularly arranged around the central axis 4 jet nozzles 2. With respect to possible arrangements of the jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.

Im Bereich der Fluidhaupteinlassöffnung 8 der Strahldüse 2 ist in den Figuren 5 bis 7 eine Brennstoffdüse 19 angeordnet. Durch die Brennstoffdüse 19 wird Brennstoff 12 in die Strahldüse 2 eingedüst. Vorzugsweise wird der Brennstoff 12 in einem Winkel von etwa 45° zur Strömungsrichtung 10 der durch die Fluidhaupteinlassöffnung 8 in die Strahldüse einströmende Druckluft 11 eingedüst. Die Strömungsrichtung des durch die Brennstoffdüse 19 eingedüsten Brennstoffes 12 ist durch Pfeile 17 gekennzeichnet. Der Brennstoff 12 kann ebenso in einem anderen Winkel zwischen 0° und 90° zur Strömungsrichtung 10 der Druckluft 11 in die Strahldüse 2 eingedüst werden.In the region of the fluid main inlet opening 8 of the jet nozzle 2 is in the FIGS. 5 to 7 a fuel nozzle 19 is arranged. Through the fuel nozzle 19, fuel 12 is injected into the jet nozzle 2. The fuel 12 is preferably injected at an angle of approximately 45 ° to the flow direction 10 of the compressed air 11 flowing into the jet nozzle through the main fluid inlet opening 8. The flow direction of the injected fuel nozzle 19 through the fuel 12 is indicated by arrows 17. The fuel 12 can also be injected at a different angle between 0 ° and 90 ° to the flow direction 10 of the compressed air 11 in the jet nozzle 2.

An verschiedenen axialen Positionen der Strahldüse 2 sind weitere Fluidnebeneinlassöffnungen 25 angeordnet, durch die Druckluft in die Strahldüse 2 eingedüst werden kann. Die Druckluft wird dabei über einen Ringspalt 22 zu den Fluidnebeneinlassöffnungen 25 geleitet. In den Figuren 5 und 6 wird die Druckluft durch die Fluidnebeneinlassöffnungen 25 senkrecht zur Mittelachse 5 der Strahldüse in die Strahldüse 2 eingedüst. Dabei strömt in der Figur 5 die von einem Kompressor kommende Druckluft in Richtung des Pfeils 15 durch den Ringspalt 22.At different axial positions of the jet nozzle 2 further fluid sub-inlet openings 25 are arranged, can be injected by the compressed air into the jet nozzle 2. The compressed air is passed through an annular gap 22 to the fluid sub-inlet openings 25. In the Figures 5 and 6 the compressed air is injected into the jet nozzle 2 through the fluid sub-inlet openings 25 perpendicular to the central axis 5 of the jet nozzle. It flows in the FIG. 5 Coming from a compressor compressed air in the direction of arrow 15 through the annular gap 22nd

In der Figur 6 wird die von einem Kompressor kommende Druckluft durch eine Lufteinlassöffnung 23 senkrecht zur Mittelachse 5 der Strahldüse 2 in den Brenner 301 eingedüst. Die Strömungsrichtung der die Öffnung 23 passierenden Druckluft 11 ist durch einen Pfeil 26 gekennzeichnet. Die Druckluft 11 strömt nun durch den Ringspalt 22 zu den Fluidnebeneinlassöffnungen 25 und gelangt über diese in die Strahldüse 2. Der Hauptanteil der Druckluft 11 wird jedoch durch die Fluidhaupteinlassöffnung 8 in Strömungsrichtung 10 in die Strahldüse 2 eingeleitet.In the FIG. 6 the compressed air coming from a compressor is injected through an air inlet opening 23 perpendicular to the central axis 5 of the jet nozzle 2 in the burner 301. The flow direction of the opening 23 passing compressed air 11 is indicated by an arrow 26. The compressed air 11 now flows through the annular gap 22 to the fluid sub-inlet openings 25 and passes through them into the jet nozzle 2. However, the majority of the compressed air 11 is introduced into the jet nozzle 2 through the main fluid inlet opening 8 in the flow direction 10.

Die Figur 7 zeigt eine alternative Ausgestaltung des in der Figur 5 gezeigten Brenners 301. Im Unterschied zu der Figur 5 sind in der Figur 7 die Fluidnebeneinlassöffnungen 25 so angeordnet, dass die durch die Fluidnebeneinlassöffnungen 25 in die Strahldüse 2 eingedüste Druckluft in einem Winkel von etwa 45° zur Mittelachse 5 des Strahlrohres 2 in dieses eingedüst wird. Grundsätzlich ist auch ein anderer Eindüswinkel zwischen 0° und 90° möglich und sinnvoll.The FIG. 7 shows an alternative embodiment of the in the FIG. 5 shown burner 301. In contrast to the FIG. 5 are in the FIG. 7 the fluid sub-inlet openings 25 are arranged in that the compressed air injected into the jet nozzle 2 through the secondary fluid inlet openings 25 is injected into the compressed air at an angle of approximately 45 ° to the central axis 5 of the jet tube 2. Basically, another Eindüswinkel between 0 ° and 90 ° is possible and useful.

Die für die axial gestufte Lufteindüsung des vorliegenden Ausführungsbeispieles verwendete Luft kann entweder aus dem Ringspalt 22 oder direkt aus einem den Brenner 301 umgebenden Plenum entnommen werden und in das Brennstoff-Luft-Gemisch in der Strahldüse eingedüst werden. Die Luft kann dabei als Strahl in die Querströmung oder als Wandfilm eingebracht werden. Der Vorteil einer Strahl-in-Querströmungseindüsung ist ein Beitrag zu einer erhöhten Mischung des Brennstoff-LuftGemisches, während eine Wandfilmbildung vor allem eine Maßnahme gegen einen möglichen Flammenrückschlag ist. Weiterhin kann die Luft tangential in Bezug auf den Umfang der Strahldüse 2 in diese eingedüst werden. Dabei kann auf der kompletten inneren Oberfläche der Strahldüse 2 ein Wandfilm erzeugt werden. Ein tangentiales Eindüsen kann zudem zur Wirbelerzeugung in der Strahldüse 2 genutzt werden.The air used for the axially stepped Lufteindüsung of the present embodiment can be removed either from the annular gap 22 or directly from a surrounding the burner 301 plenum and are injected into the fuel-air mixture in the jet nozzle. The air can be introduced as a jet in the cross flow or as a wall film. The advantage of jet-in-cross-flow injection is a contribution to increased mixing of the fuel-air mixture, while wall-film formation is primarily a measure against potential flashback. Furthermore, the air can be injected tangentially with respect to the circumference of the jet nozzle 2 in this. In this case, a wall film can be produced on the entire inner surface of the jet nozzle 2. Tangential injection can also be used to generate turbulence in the jet nozzle 2.

Denkbar ist auch eine Strahl-in-Querströmungseindüsung mit einer Wandfilmeindüsung zu kombinieren, indem die Düsen sehr kurz hintereinander angeordnet sind. Die Strahl-in-Querströmungseindüsung sorgt für eine verbesserte Mischung, vor allem auch im Kernbereich des Strahls, und der Film der zweiten Düse stärkt die Strömungsgrenzschicht und verhindert somit einen Flammenrückschlag. Diese Ausgestaltung ist insbesondere vorteilhaft für eine zentrale Co-Flow-Eindüsung in der Hauptbrennstoffeindüsung, zum Beispiel für Synthesegas. Bei einem hohen Luftanteil in der axialen Stufung ist es möglich, die Düsendurchmesser der Strahldüse so anzupassen, dass die Strömungsgeschwindigkeit in der Düse im Wesentlichen gleich bleibt.It is also conceivable to combine a jet-in-cross-flow injection with a wall-film injection by arranging the nozzles very shortly after one another. The jet-in-cross flow injection provides for improved mixing, especially in the core region of the jet, and the film of the second jet strengthens the flow boundary layer and thus prevents flashback. This embodiment is particularly advantageous for a central co-flow injection in the Hauptbrennstoffeindüsung, for example for synthesis gas. With a high proportion of air in the axial staging, it is possible to adjust the nozzle diameter of the jet nozzle so that the flow velocity in the nozzle remains substantially the same.

Im Folgenden wird ein drittes Ausführungsbeispiel anhand der Figuren 8 und 9 näher beschrieben. Elemente, die Elementen der ersten Ausführungsbeispiele entsprechen, sind mit denselben Bezugsziffern versehen und werden nicht erneut im Detail beschrieben.In the following, a third embodiment based on the FIGS. 8 and 9 described in more detail. Elements, the elements correspond to the first embodiments, are provided with the same reference numerals and will not be described again in detail.

Die Figuren 8 und 9 zeigen schematisch verschiedene Varianten eines Brenners 401 in Längsrichtung entlang der Mittelachse 4 des Brenners 401. Der Brenner 401 weist eine Anzahl Strahldüsen 2 auf, die im Wesentlichen ringförmig um die Mittelachse 4 des Brenners 401 angeordnet sind. In Bezug auf mögliche Anordnungen der Strahldüsen 2, 3 wird auf die Figuren 1 und 2 und die in diesem Zusammenhang gemachten Ausführungen verwiesen.The FIGS. 8 and 9 schematically show various variants of a burner 401 longitudinally along the central axis 4 of the burner 401. The burner 401 has a number of jet nozzles 2, which are arranged substantially annularly around the central axis 4 of the burner 401. With respect to possible arrangements of the jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.

Jede Strahldüse 2 umfasst eine Fluidhaupteinlassöffnung 8 und eine Fluidauslassöffnung 9. Die Fluidauslassöffnung 9 mündet in die Brennkammer 18. In der Fluidhaupteinlassöffnung 8 ist eine Brennstoffdüse 19 angeordnet. Die Brennstoffdüse 19 umfasst einen Brennstoffverteiler 20, mit dessen Hilfe an verschiedenen radialen Positionen und verschiedenen Umfangspositionen der Fluidhaupteinlassöffnung 8 Brennstoff 12 in die Strahldüse 2 eingedüst werden kann. Die Strömungsrichtung des eingedüsten Brennstoffes 12 ist durch Pfeile 17 gekennzeichnet.Each jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9. The fluid outlet opening 9 opens into the combustion chamber 18. A fuel nozzle 19 is arranged in the main fluid inlet opening 8. The fuel nozzle 19 comprises a fuel distributor 20 with the aid of which fuel 12 can be injected into the jet nozzle 2 at different radial positions and different circumferential positions of the main fluid inlet opening 8. The flow direction of the injected fuel 12 is indicated by arrows 17.

An einer weiteren stromabwärts in Bezug auf die Strömungsrichtungen 10 und 17 gelegenen axialen Position der Strahldüse 2 ist ein Ringspalt 21 angeordnet. Durch den Ringspalt 21 wird Luft in die Strahldüse 2 eingedüst. Die Strömungsrichtung der eingedüsten Luft ist durch Pfeile 16 gekennzeichnet. Die Luft wird dabei nahezu parallel zu der Mittelachse 5 der Strahldüse 2 in diese eingedüst. Im Unterschied zu der in der Figur 8 gezeigten Variante ist in der Figur 9 der Ringspalt 21 an einer stromabwärts von der Fluidhaupteinlassöffnung 8 weiter entfernt gelegenen Position angeordnet. In beiden in den Figuren 8 und 9 gezeigten Varianten kann die verwendete Druckluft von einem Kompressor entweder durch einen Ringspalt 22 in Strömungsrichtung 15 zur Fluidhaupteinlassöffnung 8 der Strahldüse 2 geleitet werden und/oder senkrecht zur Mittelachse 5 in Strömungsrichtung 26 eingedüst werden.At a further downstream with respect to the flow directions 10 and 17 located axial position of the jet nozzle 2, an annular gap 21 is arranged. Air is injected into the jet nozzle 2 through the annular gap 21. The direction of flow of the injected air is indicated by arrows 16. The air is injected almost parallel to the central axis 5 of the jet nozzle 2 in this. Unlike the one in the FIG. 8 shown variant is in the FIG. 9 the annular gap 21 is disposed at a position further downstream of the main fluid inlet port 8. In both in the FIGS. 8 and 9 In the variants shown, the compressed air used can be directed by a compressor either through an annular gap 22 in the flow direction 15 to the main fluid inlet opening 8 of the jet nozzle 2 and / or vertically be injected to the central axis 5 in the flow direction 26.

Die in den Figuren 8 und 9 gezeigten Ausführungsvarianten beinhalten die Möglichkeit, den stromabwärts in Bezug auf die Strömungsrichtung 15 der vom Kompressor kommenden Druckluft gelegenen Düsenteil, an dem auch die Brennstoffverteilung hängt, von der Rückwand 24 des Brenners aus in den Brenner 401 zu stecken und diesen durch den vorderen, brennkammerseitigen Teil zu positionieren, zum Beispiel durch Abstandhalter in dem Ringraum. Im Extremfall sitzt der stromabwärts gelegene Düsenteil direkt im Flammrohrboden.
Die Fig. 10 zeigt einen Querschnitt eines Stahlbrenners 1 sowie des Ringverteilers 7 mit mehreren radialen Fluidnebeneinlassöffnungen 14. Der Ringverteiler 7 umfaßt dabei einen kompletten Kranz von Strahldüsen 2. Von den Ringverteiler 7 gehen Fluidnebeneinlassöffnungen 14 ab, die die Strahldüsen 2 an unterschiedlichen Umfangspositionen treffen. Dabei können lange Fluidnebeneinlassöffnungen 14 angestellt werden. Auch können Fluidnebeneinlassöffnungen 14 einen Winkel zur Strahldüse 2 aufweisen. Die Strahldüsen 2 können dabei beliebig angeordnet sein. Auch ist vorstellbar dass lediglich ein außenliegender Ringverteiler 7 mit Brennstoff vorliegt und die Strahldüsen in dessen inneren beliebig angeordnet sind (zentraler Strahlbrenner 1).The in the FIGS. 8 and 9 embodiments shown include the possibility of the downstream with respect to the flow direction 15 of the compressed air from the compressor located nozzle part, which also depends on the fuel distribution, stuck from the rear wall 24 of the burner in the burner 401 and this through the front, combustion chamber side part to position, for example by spacers in the annulus. In extreme cases, the downstream nozzle part sits directly in the bottom of the flame tube.
The Fig. 10 shows a cross section of a steel burner 1 and the ring manifold 7 with a plurality of radial fluid sub-inlet openings 14. The ring manifold 7 thereby comprises a complete ring of jet nozzles 2. From the ring manifold 7 go from Fluidnebeneinöffnungen openings 14, which meet the jet nozzles 2 at different circumferential positions. In this case, long fluid secondary inlet openings 14 can be made. Also, secondary fluid inlet ports 14 may be at an angle to the jet nozzle 2. The jet nozzles 2 can be arranged arbitrarily. It is also conceivable that only an external ring distributor 7 is present with fuel and the jet nozzles are arranged arbitrarily in the interior (central jet burner 1).

Der erfindungsgemäße Brenner 201, 301, 401 kann in allen Ausführungsbeispielen und Ausführungsvarianten auch ohne den äußeren Gehäuseteil 27 beziehungsweise ohne äußeres Gehäuse 27 ausgestaltet sein. In diesem Fall kann die Druckluft direkt in das "Plenum", also den Bereich zwischen der Rückwand 24 und der Fluidhaupteinlassöffnung 8, strömen. Der erfindungsgemäße Brenner 1, 101, 201, 301, 401 kann weiterhin auch ohne die Rückwand 24 ausgestaltet sein.The burner 201, 301, 401 according to the invention can also be designed without the outer housing part 27 or without the outer housing 27 in all exemplary embodiments and variants. In this case, the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8. The burner 1, 101, 201, 301, 401 according to the invention can furthermore be designed without the rear wall 24.

Durch eine Variation der axialen Positionen der Ringspalte 21 wird ein zusätzlicher Designparameter gegen thermoakustische Flammenschwingungen gewonnen. Außerdem besteht die Möglichkeit, die unterschiedlichen Strahldüsen 2 eines Brenners 401 mit Ringspalten 21 an unterschiedlichen axialen Positionen zu versehen.By varying the axial positions of the annular gaps 21, an additional design parameter against thermoacoustic flame oscillations is obtained. It is also possible to provide the different jet nozzles 2 of a burner 401 with annular gaps 21 at different axial positions.

Claims (20)

  1. Method for reducing self-induced flame oscillations, wherein, into a first mass flow of fluid comprising air (11) and flowing through a jet nozzle (2, 3) from a fluid inlet opening (8) to a fluid outlet opening (9),
    there is injected a second mass flow of fluid comprising a fuel (12) at at least one axial position on the jet nozzle (2, 3) downstream of the fluid inlet opening (8),
    characterised in that, from the fuel line (22) from which the first mass flow of fluid flows into the jet nozzle (2, 3), a third mass flow of fluid is additionally injected into the first mass flow of fluid at a plurality of positions disposed mutually offset in the axial direction around the circumference of the jet nozzle (2, 3).
  2. Method for reducing self-induced flame oscillations, wherein, into a first mass flow of fluid comprising air (11) and flowing through a jet nozzle (2, 3) from a fluid inlet opening (8) to a fluid outlet opening (9),
    there is injected a second mass flow of fluid comprising a fuel (12) at at least one radial position on the jet nozzle (2, 3) with respect to the circumference of the jet nozzle (2),
    characterised in that, from the fuel line (22) from which the first mass flow of fluid flows into the jet nozzle (2, 3), a third mass flow of fluid is additionally injected into the first mass flow of fluid at a plurality of positions disposed mutually offset in the axial direction around the circumference of the jet nozzle (2, 3).
  3. Method according to claim 2,
    characterised in that different radial fuel distributions are implemented.
  4. Method according to claims 1 to 3,
    wherein the second mass flow of fluid is injected into the first mass flow of fluid at a plurality of positions around the circumference of the jet nozzle (2, 3).
  5. Method according to claim 4,
    wherein the second mass flow of fluid is injected into the first mass flow of fluid at a plurality of positions disposed mutually offset in the axial direction around the circumference of the jet nozzle (2, 3).
  6. Method according to one of claims 1 to 5,
    wherein the second mass flow of fluid comprising a fuel is an air/fuel mixture.
  7. Method according to one of claims 1 to 6,
    wherein the second and/or the third mass flow of fluid is injected into the first mass flow of fluid at an angle of between 0° and 90°.
  8. Method according to claim 7,
    wherein the second mass flow of fluid is injected into the first mass flow of fluid at an angle of 90° and the third mass flow of fluid is injected into the first mass flow of fluid at an angle of 45°.
  9. Burner (1, 101, 201, 301, 401),
    comprising at least one jet nozzle (2, 3) with a main fluid inlet opening (8) and a fluid outlet opening (9), wherein the main fluid inlet opening (8) is connected to a first fluid supply line (22) which is an air supply line,
    wherein fuel can be injected into the jet nozzle (2, 3) either via a fuel nozzle (19) which is disposed in or immediately preceding the main fluid inlet opening (8), or via at least one axial position on the jet nozzle (2, 3) downstream of the main fluid inlet opening (8) and with a first fluid inlet opening (14) connected to a fluid supply line (7, 13), characterised in that second secondary fluid inlet openings (21, 25) are connected to the first fluid supply line (22) and disposed at a plurality of positions disposed in a mutually offset manner in the axial direction along the circumference of the jet nozzle (2, 3).
  10. Burner (1, 101, 201, 301, 401),
    comprising at least one jet nozzle (2, 3) with a main fluid inlet opening (8) and a fluid outlet opening (9), wherein the main fluid inlet opening (8) is connected to a first fluid supply line (22) which is an air supply line,
    wherein fuel can be injected into the jet nozzle (2, 3) either via a fuel nozzle (19) which is disposed in or immediately preceding the main fluid inlet opening (8), or via at least one radial position of the jet nozzle with respect to the circumference of the jet nozzle (2) and with a first secondary fluid inlet opening (14) connected to a fluid supply line (7, 13),
    characterised in that second secondary fluid inlet openings (21, 25) are connected to the first fluid supply line (22) and disposed at a plurality of positions disposed in a mutually offset manner in the axial direction along the circumference of the jet nozzle (2, 3).
  11. Burner (1, 101, 201, 301, 401) according to claim 9 or 10, characterised in that first secondary fluid inlet openings (14) are disposed at a plurality of positions along the circumference of the jet nozzle (2, 3).
  12. Burner (1, 101, 201, 301, 401) according to claims 9 to 11,
    characterised in that first secondary fluid inlet openings (14) are disposed at a plurality of positions disposed in a mutually offset manner along the circumference of the jet nozzle (2, 3).
  13. Burner (1, 101, 201, 301, 401) according to one of claims 9 to 12,
    characterised in that the first or second secondary fluid inlet openings (14, 21, 25) and the main fluid inlet opening (8) each have a central axis and the central axes of the first or second secondary fluid inlet openings (14, 21, 25) are at an angle of between 0° and 90° to the central axis of the main fluid inlet opening (8) and/or to the central axis (5) of the jet nozzle (2, 3).
  14. Burner (1, 101, 201, 301, 401) according to claim 13, characterised in that the central axes of a first portion of the first or second secondary fluid inlet openings (14, 21, 25) are at an angle of 90° to the central axis of the main fluid inlet opening (8) and/or to the central axis (5) of the jet nozzle (2, 3), and the central axes of a second portion of the first or second secondary fluid inlet openings (14, 21, 25) are at an angle of 45° to the central axis of the main fluid inlet opening and/or to the central axis (5) of the jet nozzle (2, 3).
  15. Burner (1, 101, 201, 301, 401) according to one of claims 9 to 14, characterised in that
    the first or second secondary fluid inlet openings (14, 21, 25) and the main fluid inlet opening (8) each have a central axis and the central axes of the first or second secondary fluid inlet openings (14, 21, 25) are at an angle of between 0° and 90° to a radial direction with respect to the central axis of the main fluid inlet opening (8).
  16. Burner (1, 101, 201, 301, 401) according to one of claims 9 to 21, characterised in that
    a plurality of fluid supply lines (7) connected to first secondary fluid inlet openings (14, 21, 25) are interconnected via an annular distributor (7) disposed along the circumference of the jet nozzle (2, 3).
  17. Burner (1, 101, 201, 301, 401) according to one of claims 9 to 16, characterised in that
    the fuel nozzle (19) comprises a fuel distributor (20) which is disposed in or immediately preceding the main fluid inlet opening (8).
  18. Burner (1, 101, 201, 301, 401) according to one of claims 9 to 17, characterised in that
    at least the second secondary fluid inlet opening (21) is implemented as an annular gap (21) running along the circumference of the jet nozzle (2, 3).
  19. Burner (1, 101, 201, 301, 401) according to claim 18, characterised in that
    the burner (1, 101, 201, 301, 401) is implemented as a jet burner and comprises a plurality of jet nozzles (2, 3) and the annular gaps (21) of the different jet nozzles (2, 3) are disposed at different axial positions in each case.
  20. Gas turbine comprising a burner according to claim 9 or claim 10 or claims 9 and 10.
EP08749689.9A 2008-01-11 2008-04-24 Burner and method for reducing self-induced flame oscillations Active EP2232147B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08749689.9A EP2232147B1 (en) 2008-01-11 2008-04-24 Burner and method for reducing self-induced flame oscillations

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08000497A EP2078898A1 (en) 2008-01-11 2008-01-11 Burner and method for reducing self-induced flame oscillations
EP08749689.9A EP2232147B1 (en) 2008-01-11 2008-04-24 Burner and method for reducing self-induced flame oscillations
PCT/EP2008/054969 WO2009086943A1 (en) 2008-01-11 2008-04-24 Burner and method for reducing self-induced flame oscillations

Publications (2)

Publication Number Publication Date
EP2232147A1 EP2232147A1 (en) 2010-09-29
EP2232147B1 true EP2232147B1 (en) 2015-10-28

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EP08000497A Withdrawn EP2078898A1 (en) 2008-01-11 2008-01-11 Burner and method for reducing self-induced flame oscillations
EP08749689.9A Active EP2232147B1 (en) 2008-01-11 2008-04-24 Burner and method for reducing self-induced flame oscillations

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Application Number Title Priority Date Filing Date
EP08000497A Withdrawn EP2078898A1 (en) 2008-01-11 2008-01-11 Burner and method for reducing self-induced flame oscillations

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US (1) US20100323309A1 (en)
EP (2) EP2078898A1 (en)
WO (1) WO2009086943A1 (en)

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Also Published As

Publication number Publication date
WO2009086943A1 (en) 2009-07-16
EP2078898A1 (en) 2009-07-15
US20100323309A1 (en) 2010-12-23
EP2232147A1 (en) 2010-09-29

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